Zobrazeno 1 - 10
of 14
pro vyhledávání: '"R. Manikanda Kumaran"'
Autor:
R. Manikanda Kumaran, K. Kannan, Ashok Victor, K. Tamilselvan, J. Cecily Mary Majella, R. Arun, A. Arvind, N. Viswanathan, R. Sampath Kumar, Rudrappa
Publikováno v:
Indian Heart Journal, Vol 67, Iss S1, p S8 (2015)
Externí odkaz:
https://doaj.org/article/65d9a02cbd1b422e911a5dad9bd8e7e4
Publikováno v:
Applied Thermal Engineering. 58:205-216
The present study concentrates on the effects of header design on flow mal-distribution in a micro-channel (25 channels) heat sink. Experiments have been conducted to investigate the effect of header shape (rectangular and triangular) on flow mal-dis
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::01a157e3e061516f1ffacc79c9d12d35
https://doi.org/10.1016/j.applthermaleng.2013.04.026
https://doi.org/10.1016/j.applthermaleng.2013.04.026
Publikováno v:
International Communications in Heat and Mass Transfer. 38:1349-1353
A study of flow mal-distribution in U-type micro-channel configuration is presented. Numerical simulations indicate that flow deceleration and associated pressure recovery in the inlet header lead to flow separation and recirculation which cause osci
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::ce0d35eb4b813994ee9b3e94a2dbdbf2
https://doi.org/10.1016/j.icheatmasstransfer.2011.08.020
https://doi.org/10.1016/j.icheatmasstransfer.2011.08.020
Publikováno v:
Journal of Propulsion and Power. 26:248-258
The performance of a second-throat ejector-diffuser system employed in high-altitude testing of large-area-ratio rocket motors is considered under various steady and transient operating conditions. When the diffuser attains started condition, superso
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::99e61b98d2e63fb9eb3e3dc7791588cc
https://doi.org/10.2514/1.43298
https://doi.org/10.2514/1.43298
Autor:
N. Viswanathan, A. Arvind, K Kannan, R. Arun, J. Cecily Mary Majella, Rudrappa, R. Sampath Kumar, R. Manikanda Kumaran, K. Tamilselvan, Ashok Victor
Publikováno v:
Indian Heart Journal, Vol 67, Iss S1, p S8 (2015)
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::245d84288731ea2dc3a660fa40bc8b2d
http://www.sciencedirect.com/science/article/pii/S0019483215004630
http://www.sciencedirect.com/science/article/pii/S0019483215004630
Publikováno v:
IndraStra Global.
In the present study, performance characteristics of a high altitude test facility for testing large area ratio rocket engines have been investigated. Steady-state numerical simulations have been performed initially to highlight the effects of operat
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::2e71f4c0f8d62438b8897e2ac1b06059
http://hdl.handle.net/11717/14076
http://hdl.handle.net/11717/14076
Publikováno v:
IndraStra Global.
The performance of a two-stage ejector during high-altitude testing of large-area-ratio satellite thrusters is numerically investigated. Since the flow rateof the exhaust from the satellite thrusterisvery low, self-ejector action of the exhaust is qu
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::91dc4b996d1f9ae5e203e2e6df210c0c
http://hdl.handle.net/11717/13907
http://hdl.handle.net/11717/13907
Autor:
K. Kumaresan, D. Raja Manohar, R. Manikanda Kumaran, P. K. Vivekanand, Thirumalachari Sundararajan
Publikováno v:
IndraStra Global.
In the present work, a second throat ejector using nitrogen as the primary fluid is considered for the creation of a low vacuum in a high-altitude testing facility for large-area-ratio rocket motors. Detailed numerical investigations have been carrie
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::3e4d5b36caa9580eee8afca029cc0e3e
http://hdl.handle.net/11717/11254
http://hdl.handle.net/11717/11254
Autor:
Thirumalachari Sundararajan, R. Manikanda Kumaran, Kumaresan Vivekanand, S. Balasubramanian, Raja Manohar, S. Rajarathnam
Publikováno v:
26th AIAA Applied Aerodynamics Conference.
This paper describes the influence of back pressure on the performance of a second throat ejector-diffuser system. Second throat ejector-diffuser (STED) is a subsystem in the high altitude test facility of large area ratio rocket motors. STED is empl
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::058383570e0a5a8617a5e048bf50dba1
https://doi.org/10.2514/6.2008-6588
https://doi.org/10.2514/6.2008-6588
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